RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_wing
parasite_drag_wing#
- parasite_drag_wing(state, settings, geometry)[source]#
Computes the parasite drag due to wings
Assumptions: Basic fit
Source: http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)
Args: settings.wing_parasite_drag_form_factor [Unitless] state.conditions.freestream.
mach_number [Unitless] temperature [K] reynolds_number [Unitless]
- geometry.
areas.reference [m^2] chords.mean_aerodynamic [m] thickness_to_chord [Unitless] sweeps.quarter_chord [radians] aspect_ratio [Unitless] spans.projected [m] areas.affected [m^2] areas.wetted [m^2] transition_x_upper [Unitless] transition_x_lower [Unitless]
Returns: wing_parasite_drag [Unitless]
- compute_parasite_drag(re, mac_w, Mc, Tc, xtu, xtl, sweep_w, t_c_w, Sref, Swet, C)[source]#
Computes the parasite drag due to wings
Assumptions: Basic fit
Source: adg.stanford.edu (Stanford AA241 A/B Course Notes)
Args: re (Reynolds Number) [Unitless] mac_w (Wing MAC) [m] Mc (Mach Number) [Unitless] Tc (Temperature) [K] xtu (Upper Transition) [Unitless] (percent of chord) xtl (Lower Transition) [Unitless] (percent of chord) sweep_w (Wing Sweep) [rad] t_c_w (Wing t/c) [Unitless] Sref (Wing Ref Area) [m^2] Swet (Wing Wetted Area) [m^2] C (Form Factor) [Unitless]
Returns: (u is upper, l is lower) wing_parasite_drag [Unitless] k_w (Form Factor) [Unitless] cf_w_u (Skin Friction Coefficient) [Unitless] cf_w_l [Unitless] k_comp_u (Compressibility Factor) [Unitless] k_comp_l [Unitless] k_reyn_u (Reynolds Factor) [Unitless] k_reyn_l [Unitless]